A blade track for a gas turbine engine includes segments and joints that couple the segments together. Each segment extends part-way around a central axis of the engine and the joints couple together adjacent segments to form a full hoop.
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17. A method of making a full-hoop blade track for a gas turbine engine assembly, the method comprising
inserting a circumferentially-extending tongue formed by an end portion of a first segment into a circumferentially-extending groove formed by an end portion of a second segment, and
brazing the first segment to the second segment with braze along an interface circumferentially between the first segment and the second segment to form a joint, the interface including the circumferentially extending tongue and the circumferentially-extending groove,
wherein the first segment and the second segment comprise ceramic-matrix composite materials and the circumferentially-extending tongue and the circumferentially-extending groove are configured so that one-third or less of the interface between the first segment and the second segment is engaged by the braze at any circumferential cross-sectional location of the joint,
wherein the circumferentially-extending tongue is configured to form steps when viewed inwardly in a radial direction toward a central axis.
8. A full-hoop blade track for a gas turbine engine assembly, the blade track comprising
a first segment comprising ceramic-matrix composite materials and shaped to extend part-way around a central axis, the first segment having a first circumferential end portion and a second circumferential end portion, and
a second segment comprising ceramic-matrix composite materials and shaped to extend part-way around the central axis, the second segment having a first circumferential end portion and a second circumferential end portion, and
a joint including a tongue formed by the second circumferential end portion of the first segment, a groove shaped to receive the circumferentially-extending tongue formed by the first circumferential end portion of the second segment, and a layer of bonding material arranged at an interface formed circumferentially between the first segment and the second segment,
wherein the tongue and the groove are configured so that one-third or less of the interface between the first segment and the second segment is engaged by the layer of bonding material at any circumferential cross-sectional location,
wherein the tongue is spaced apart from a forward axial face of the first segment and from an aft axial face of the first segment and the tongue is spaced apart from an outer radial face of the first segment and from an inner radial face of the first segment.
1. A full-hoop blade track for a gas turbine engine, the blade track comprising
a first segment comprising ceramic-matrix composite materials and shaped to extend part-way around a central axis, the first segment having a first circumferential end portion and a second circumferential end portion, and
a second segment comprising ceramic-matrix composite materials and shaped to extend part-way around the central axis, the second segment having a first circumferential end portion and a second circumferential end portion, and
a joint including a circumferentially-extending tongue formed by the second circumferential end portion of the first segment, a circumferentially-extending groove formed by the first circumferential end portion of the second segment and shaped to receive the circumferentially-extending tongue, and a layer of bonding material arranged at an interface formed circumferentially between the first segment and the second segment to fix the first segment to the second segment,
wherein the circumferentially-extending tongue and the circumferentially-extending groove are configured so that one-third or less of the interface between the first segment and the second segment is engaged by the layer of bonding material at any circumferential cross-sectional location,
wherein the circumferentially-extending tongue is configured to form a generally triangular shape when viewed inwardly in a radial direction toward the central axis.
2. The full-hoop blade track of
3. The full-hoop blade track of
4. The full-hoop blade track of
5. The full-hoop blade track of
6. The full-hoop blade track of
7. The full-hoop blade track of
9. The full-hoop blade track of
10. The full-hoop blade track of
11. The full-hoop blade track of
12. The full-hoop blade track of
13. The full-hoop blade track of
14. The full-hoop blade track of
15. The full-hoop blade track of
16. The full-hoop blade track of
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This application is a continuation of U.S. Non-Provisional patent application Ser. No. 15/094,502, filed Apr. 8, 2016, which claims priority to and the benefit of U.S. Provisional Patent Application Ser. No. 62/154,440, filed 29 Apr. 2015, the disclosures of which are now expressly incorporated herein by reference.
The present disclosure relates generally to gas turbine engines, and more specifically to blade tracks used in gas turbine engines.
Gas turbine engines are used to power aircraft, watercraft, power generators, and the like. Gas turbine engines typically include a compressor, a combustor, and a turbine. The compressor compresses air drawn into the engine and delivers high pressure air to the combustor. In the combustor, fuel is mixed with the high pressure air and is ignited. Products of the combustion reaction in the combustor are directed into the turbine where work is extracted to drive the compressor and, sometimes, an output shaft. Left-over products of the combustion are exhausted out of the turbine and may provide thrust in some applications.
Compressors and turbines typically include alternating stages of static vane assemblies and rotating wheel assemblies that perform work on or extract work from gasses moving through a primary gas path of the engine. The rotating wheel assemblies include disks carrying blades around their outer edges. When the rotating wheel assemblies turn, tips of the blades move along blade tracks that are arranged around the rotating wheel assemblies. Such blade tracks are adapted to reduce the leakage of gas over the blades without interaction with the blades. The blade tracks may also be designed to minimize leakage of gas into or out of the primary gas path. Design and manufacture of such blade tracks from composite material, such as ceramic-matrix composites, can present challenges.
The present disclosure may comprise one or more of the following features and combinations thereof.
According to one aspect of the present disclosure, a full-hoop blade track for a gas turbine engine includes a first segment, a second segment, and a joint that couples the first segment with the second segment. The first segment and second segment form a tongue and groove interface.
The first segment may comprise ceramic-matrix composite materials and may be shaped to extend part-way around a central axis. The first segment includes a first and a second circumferential end portion. The second segment may comprise ceramic-matrix composite materials and may be shaped to extend part-way around the central axis. The second segment includes a first and a second circumferential end portion. The joint may include a circumferentially-extending tongue formed by the second circumferential end portion of the first segment, a circumferentially-extending groove formed by the first circumferential end portion of the second segment and shaped to receive the circumferentially-extending tongue, and a layer of bonding material arranged at an interface formed circumferentially between the first segment and the second segment to fix the first segment to the second segment.
These and other features of the present disclosure will become more apparent from the following description of the illustrative embodiments.
For the purposes of promoting an understanding of the principles of the disclosure, reference will now be made to a number of illustrative embodiments illustrated in the drawings and specific language will be used to describe the same.
The turbine 18 illustratively includes a plurality of turbine stages. A turbine stage includes a turbine wheel assembly 22 and a blade track 28 (sometimes called seal ring) as shown in
The blade track 28 includes track segments 30 and joints 32 that integrally bond the track segments 30 into a full hoop as shown in
Referring to
Illustratively, each joint 32 includes a biscuit 34 (sometimes called a disk) as shown in
The second circumferential end face 40 of the first track segment 30A and the first circumferential end face 38 of the second track segment 30B face one another. As shown in
As shown in
In the illustrative embodiment, the end faces 38, 40 of the track segments 30 are formed to include blind slots 44 as shown in
Each blind slot 44 is spaced apart radially from the outer radial face 50 and the inner radial face 52 of the track segment 30 to locate the blind slot 44 therebetween as shown in
As shown in
Each joint 32 further includes a bonding material. Illustratively, the bonding material comprises braze material 36 as shown in
In some embodiments, the track segments 30 and joints 32 are joined together via a brazing process or co-processing. In some embodiments, the track segments 30 and biscuits 34 undergo CVI processing. In some embodiments, the track segments 30 and biscuits 34 are processed through slurry infiltration. In some embodiments, the track segments 30 and biscuits 34 are processed through melt infiltration. The biscuits 34 may provide improved strength over a matrix only/braze only joint. In some embodiments, the biscuits 34 and the track segments 34 may be integrally joined. In other embodiments, the track segments 30 and biscuits 34 are processed/densified as individual components and then assembled and brazed together.
In some embodiments, the inner radial faces 52 of the blade track 28 are machined relative to the full hoop. As such, greater manufacturing tolerances and tight flow path tolerances may be obtained. Machining blade track 28 may be performed before or after a coating process in which at least one face of blade track 28 is coated with a layer of coating material. In some embodiments, the coating layer is an abraidable coating. In some embodiments, end faces 38, 40 are machined.
In some embodiments, the blade track 28 includes cross-key features to mount the blade track 28 concentric with the central axis 20. The cross-key mounting may allow the blade track 28 to feely grow radially relative to a supporting case while maintaining concentricity with the central axis 20.
According to an aspect of the disclosure, a method of assembling a gas turbine engine assembly 10 may include a number of steps. The method includes inserting the biscuit 34 into the track segment 30A comprising ceramic-matrix composite materials along the end face 40 of the first track segment 30A and into the second track segment 30B comprising ceramic-matrix composite materials along the end face 38 of the second track segment 30B and brazing the biscuit 34 to the first track segment 30A and to the second track segment 30B to fix the second track segment 30B to the first track segment 30A.
Another illustrative blade track 128 is shown in
The blade track 128 includes track segments 130 and joints 132 as shown in
Each track segment 130 is formed to include a first blind slot 44A, a second blind slot 44B, a third blind slot 144C, and a fourth blind slot 144D. The first and third blind slots 144A, 144C extend into the track segments 130 from the second circumferential end face 140 toward the first circumferential end face 138. The second and fourth blind slots 144B, 144D extend into the track segments 130 from the first circumferential end face 138 toward the second circumferential end face 140.
Each blind slot 144 is spaced apart radially from the outer radial face 150 and the inner radial face 152 of the track segment 130 to locate the blind slot 144 therebetween as shown in
Illustratively, each joint 132 includes two biscuits 134A, 134B as shown in
In the illustrative embodiment, each blind slot 144 is shaped to match the contour of a corresponding biscuit 134. As shown in
According to an aspect of the disclosure, a method of assembling a gas turbine engine assembly 10 may include a number of steps. The method includes inserting the first biscuit 134A into the first track segment 130A comprising ceramic-matrix composite materials along the end face 140 of the first track segment 130A and into the second track segment 130B comprising ceramic-matrix composite materials along the end face 138 of the second track segment 130B and brazing the first biscuit 134A to the first track segment 130A and to the second track segment 130B to fix the second track segment 130B to the first track segment 130A.
The method may further include inserting the second biscuit 134B, spaced from the first biscuit 134A, into the first track segment 130A along the end face 140 of the first track segment 130A and into the second track segment 130B along the end face 138 of the second track segment 130B. The method may further include brazing the second biscuit 134B to the first track segment 130A and to the second track segment 130B.
Another illustrative blade track 228 is shown in
As shown in
Another illustrative blade track 328 is shown in
As shown in
Another illustrative blade track 428 is shown in
The blade track 428 includes track segments 430 located circumferentially adjacent to one another to form a full hoop around the central axis 20 and joints 432 that couples the track segments 430 together to fix the track segments 430 in place relative to one another. Referring to
Illustratively, each joint 432 includes a circumferentially-extending tongue 466, a corresponding circumferentially-extending groove 468, and a layer of bonding material 436 as shown in
In illustrative embodiments, the circumferentially-extending tongue 466 and the circumferentially-extending groove 468 are shaped so that less than half of the interface 476 between the first track segment 430A and the second track segment 430B is available to be engaged by the layer of bonding material 436 at any circumferential cross-sectional location. In some embodiments, the circumferentially-extending tongue 466 and the circumferentially-extending groove 468 are shaped so that one-third or less of the interface 476 between the first track segment 430A and the second track segment 430B is available to be engaged by the layer of bonding material 436 at any circumferential cross-sectional location as shown, for example, in
As shown in
The circumferentially-extending tongue 466 includes a circumferential end 474 as shown in
A method of making a gas turbine engine assembly in accordance with the present disclosure may include a number of steps. The method may include inserting the circumferentially-extending tongue 466 formed by the end portion 460 of the first track segment 430A into the circumferentially-extending groove 468 formed by the end portion 458 of the second track segment 430B and brazing the first track segment 430A to the second track segment 430B along the interface 476 circumferentially between the first track segment 430A and the second track segment 430B to form the joint 432. The interface 476 including the circumferentially-extending tongue 466 and the circumferentially-extending groove 468. The first track segment 430A and the second track segment 430B comprise ceramic-matrix composite materials. The circumferentially-extending tongue 466 and the circumferentially-extending groove 468 are shaped so that one-third or less of the interface 476 between the first track segment 430A and the second track segment 430B is available to be engaged by the braze 436 at any circumferential cross-sectional location of the joint 432.
Another illustrative blade track 528 is shown in
Another illustrative blade track 628 is shown in
The circumferentially-extending tongue 666 is shaped to form a plurality of teeth 672 when viewed inwardly in a radial direction toward the central axis 20. In the illustrative embodiment, the teeth 672 are triangular shape.
Another illustrative blade track 728 is shown in
As shown in
The circumferentially-extending tongue 766 is spaced apart radially from the outer radial face 750 and the inner radial face 752 of the track segment 730 as shown in
The circumferentially-extending groove 768 is spaced apart radially from the outer radial face 750 and the inner radial face 752 of the track segment 730 to locate the circumferentially-extending groove 768 therebetween as shown in
While the disclosure has been illustrated and described in detail in the foregoing drawings and description, the same is to be considered as exemplary and not restrictive in character, it being understood that only illustrative embodiments thereof have been shown and described and that all changes and modifications that come within the spirit of the disclosure are desired to be protected.
Thomas, David J., Sippel, Aaron D., Eifert, Andrew J., Vetters, Daniel K., Shi, Jun, Broadhead, Peter
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